Abstract: The present variable airfoil assembly has an adjustable airfoil member pivotally mounted in the top of a fixed airfoil member for adjustment between a fully lowered position (for minimum wind resistance) and different raised positions in which it projects up above the top surface of the fixed airfoil member to control the lift and drag. A minimum clearance between the fixed and adjustable airfoil members is provided at the front end of the adjustable airfoil member over a range of its pivotal adjustments. The variable airfoil assembly is capable of increasing the lift of the airfoil, then lowering stalling speed, and it may either replace flaps or be used in conjunction with flaps. Higher cruise speeds can be achieved as well as good low speed performance.
Abstract: A variable span wing in which a movable wing segment is externally mounted to slide along the trailing edge of the stationary main wing. The movable wing segment is extended beyond the span of the main wing at subsonic flight and retracted to the same span at supersonic flight. Extension (or retraction) on one side only provides roll control. Retraction subsonic speeds is utilized to achieve improved ride qualities and a reduction in wing loads at high load factors.
Abstract: A flap such as an aileron or a landing flap is operatively secured to the rear edge of an aircraft wing in such a manner that the wing construction itself may be thin in the direction perpendicularly to the central plane of the wing and as compared to the prior art wing structures. For this purpose a coupling plate extending vertically is secured to the bottom of the flap. The coupling plate provides two journal points arranged substantially vertically one above the other. The upper journal point is connected to the wing. The lower journal point is connected to a rocker drive. A drive piston rod is connected through crank levers to rotate the coupling plate in the manner of a four journal drive.
May 26, 1978
Date of Patent:
January 1, 1980
Gunther Moelter, Hermann Mueller, Ruediger Kunz
Abstract: An aircraft nose and forebody shaped to produce relatively ideal vortex patterns which will provide improved static directional stability of the aircraft in the stall angle of attack region and above. The nose is shaped from its forwardmost tip with a broad, flattened lateral cross section having relatively sharp edges extending around each lateral surface, blending rearwardly to a radius approximately midway between the top and bottom surfaces of the forebody in the region where separation of the vortices is desired.
December 7, 1978
Date of Patent:
December 4, 1979
Jack W. Headley, Andrew M. Skow, Andrew Titiriga, Jr.
Abstract: Apparatus for controlling the movement and positioning of an aircraft trim tab comprising: an elongated stabilizer member mounted in the cockpit of the aircraft for reciprocal forward and aft movement and having a threaded portion thereon; a cable member connecting the stabilizer member to the trim tab for movement and positioning thereof in response to reciprocal movement of the stabilizer member; and a control member threadedly engaging the threaded portion of the stabilizer member and manually engageable and rotatable from inside the cockpit for translating rotation of the control member to reciprocal movement of the stabilizer member.
Abstract: A system for inducing turns in ram air canopy parachutes having a plurality of openings in the upper surface layer of the parachute canopy with the openings being equally distributed on opposite sides of the parachute centerline. Flaps are provided on the under side of the upper surface layer to close the openings. Control lines are attached to the flaps for selectively opening the flaps on one or the other side of the centerline to allow ram air to flow through the openings. This reduces lift and increases drag on one side of the ram air canopy parachute to induce a turn.
Abstract: A solar powered hot air balloon is disclosed having an envelope with an opaque portion and a transparent portion arranged so as to utilize solar heating to heat air within the envelope. The solar heating air may either by sufficient to provide the entire free lift or may be combined with air from a hot air generating system carried by a gondola supported by the envelope. The opaque portion of the envelope has a substantially black inner surface and a light reflecting outer surface with the black inner surface being positioned so as to receive a maximum amount of sunlight through the transparent portion for a given average position of the sun.
Abstract: A vehicle for traveling in the air and on the ground is equipped with two, four, or eight propellers on vertical shafts, each driven by a rotary hydraulic motor of the radial-piston type. The motor comprises two rotors which are connected in individual hydraulic circuits supplied with fluid from different hydraulic pumps. One embodiment of the vehicle comprises an automobile with the propellers mounted in oblique air ducts or in shrouds pivotable in the travel direction. Each rotor of the hydraulic motors is coupled to the shaft unidirectionally so that in case of failure, the shaft can be driven by the other rotor. Each hydraulic pump preferably produces four equal fluid flows and comprises two rotors on a common shaft, each rotor with two separate groups of cylinders, the eccentricity of at least one of the rotors being adjustable. Both the hydraulic motor and the pump have inlet and outlet connections on the radial periphery of the housing.
Abstract: A pair of motion-amplifying flap linkages connected externally to the undersurface of a tapered planform airfoil and being spaced apart spanwise thereof for a combined pseudo conical extension movement of a tapered-chord flap section. The pair of flap linkage mechanisms conjointly first extending the tapered chord flap section chordwise of the airfoil and then rotatably tilting the flap to increase its angle of incidence, such that the chordwise length of movement and rotation of the flap, is proportional to the length of the airfoil chord at that cross-section of the airfoil; and approximates a conic motion of the flap relative to the airfoil.
Abstract: An exhaust stub for a turbo-prop engine which exits from the aircraft nacelle at a location other than the aft end. A fairing is attached to the exhaust stub to minimize frontal area for a given exhaust stub exit area, but free of the nacelle, because of the requirement for the exhaust stub to move relative to the nacelle. An end plate is secured about the exhaust stub and fairing, substantially parallel to and at close proximity to the nacelle. The end plate effectively improves the performance of the fairing, by eliminating the effect of the gap in the nacelle around the stub and also the gap between the fairing and the nacelle. Improving the performance of the fairing reduces the magnitude of the exhaust duct wake which in turn reduces the momentum definiency in the wake flow; reduces exhaust duct drag; reduces mixing of the exhaust gases into the wake region; and reduces nacelle sooting by exhaust gases.
Abstract: Devices to reduce the drag experienced by aircraft and other travelling bodies, comprising sail-like members mounted on the body surface. These members project into the local stream that forms close to the surface during motion, and tend to divert that local stream back into the free stream direction and in so doing to experience useful thrust. The members are cambered and the camber varies from root to tip to allow for change in the local stream direction as distance from the surface increases. Special sails for use on surfaces subject to some complex flows, adjustable sails and arrays of several sails for use especially at aircraft wing tips, are also proposed.
June 10, 1977
Date of Patent:
October 30, 1979
National Research Development Corporation
Abstract: An airfoil having a support frame, a rigid nose section, and upper and lower variable camber skin sections extending from the nose section rearwardly to the support frame. The frame has a rigid mounting arm which extends forwardly into the variable camber section, and a pivot link is connected from that mounting arm to a lower portion of the nose section so that is is able to swing downwardly and rearwardly to its cambered position. A toggle linkage connects an upper portion of the nose section to the frame just beneath the upper variable camber skin section. Flexure of the toggle linkage during downward movement of the nose section reduces the chord length of the arc of the variable camber upper skin section so that a proper continuous curve is formed by the upper variable camber skin section from the nose section back to the frame.
Abstract: A shift mechanism for an aircraft control system for reversibly shifting the control system of the aircraft between a power mode and a manual mode of operation. The shift mechanism has a stick control input connection, a primary control surface output connection and a secondary control surface output connection. The input connection is made to a bell crank-shaped housing which is pivoted to the aircraft structure and the output connections are connected to an idler arm and connecting member, respectively, that are pivoted to the housing. The connecting member is moved by an actuator between a first position wherein its pivotal connection to the secondary control surface output connection is aligned with the pivotal connection of the housing to the aircraft and a second position of non-alignment. During this second position, the primary control surface output connection is disconnected from the idler arm.
April 20, 1978
Date of Patent:
October 16, 1979
The United States of America as represented by the Secretary of the Air Force
Abstract: An aircraft has three propulsion engines, two of which each include one pivotable exhaust nozzle which are arranged one on each side of the aircraft, and a third engine including two pivotable exhaust nozzles, one of which is arranged on either side of the aircraft. The arrangements being such that upon failure of one of the two engines the efflux from the third engine is only directed through the nozzle situated on the side of the aircraft which the failed nozzle is arranged.
Abstract: The invention to be described is an aquatic apparatus of at least one hull which is readily attachable and detachable from its propulsive member--the propulsive member being a tandem-wheeled vehicle such as a bicycle or motorcycle which is prepared for attachment by having its wheels removed.
Abstract: A kite, comprising a substantially arrow-shaped body; a wing framework mounted to and divided by the body into two quadrilateral sections; a cover, respectively spanning loosely across and mounted to two opposite sides of each division of the wing framework, one of the unmounted sides thereof is provided with a reinforcing strip of material; a tail framework mounted to the body; a cover spanning loosely across and mounted at two opposite sides of the tail frame, one unmounted side thereof is provided with a reinforcing strip of material; lengths of strings are mounted to the body of the kite.
Abstract: Kite launching apparatus including a control line with a portion thereof which is elastic. A portion of a Velcro holding structure is operatively attached to the kite or the control line. A stake is provided for being anchored to the ground. Another portion of the Velcro holding structure is operatively attached to the stake whereby the two portions of Velcro can be connected together. Once the Velcro holding structure portions are connected together the launching structure can be utilized by pulling on the control line to stretch the elastic portion thereof. When enough force has been applied to the Velcro holding structure to cause the two Velcro portions to come apart, the kite is automatically launched because of the pull of the elastic portion of the control line as it returns to its original shape.
Abstract: This hoisting device for loads to be carried under aircraft is incorporated partially or completely in a load carrier system without requiring any lateral access, the connection between the hoisting device and the load being eliminated automatically once the load is properly anchored to the carrier system. The device comprises one or two ropes, as the case may be, and comprises an anchoring member rigid with the load and formed with an internal groove engageable by a set of balls carried by a socket in which an end piece crimped to the rope end is adapted to travel axially through a limited extent. Slackening the rope will free the load which is then retained by the carrier system.
Abstract: This invention is an extension of my system to recover into useful work the energy normally wasted by a supersonic aircraft in its shock wave mechanism. This system utilizes the excess propulsive jet velocity in a sheet below the wing to form a planar vortex flap which acts as a pressure shield. The present improvement extends the pressure generating forward concave wing undersurface of this system into an upward reflexed aft surface so as to benefit from the increased pressure provided by the downstream upwash vortex field. This allows the aft portion of the wing to serve as the energy recovery section by achieving the pressure required for lift on the undersurface of this aft wing portion at a lesser angle with reduced drag. This stream-wise series of functions specifies the wing undersurface as concave, convex, and concave sequentially in the flow direction, thus corresponding to the upper element of a planar supersonic nozzle.
Abstract: A lighter than air ship, with a bow plate on the bow, two cars suspended beneath the elongated bag, the cars having water ballast tanks, with scoops to take in water when the airship is landing on water and valves to let the water out when the airship is taking off, with a sea anchor and rode (rope) to the bow plate, a ground (bottom) anchor and rode (rope) to the bow plate, metal ribs attached to the bow plate and extending to a stern plate and connected to the bag both above and below the bag, with a vertical rudder for steering right and left, horizontal rudders for steering up and down and a ballonet inside the bag for keeping proper pressure, landing wheels for landing the airship on land, the cars being capable of landing the airship on water, the bag having an aerodynamic lifting shape so that the airship can take off and fly heavy and by dumping water can land safey and landing on water can take in water to be stable on the surface, can land on land with the wheels and be secured by the rodes.